EP2253801A1

EP2253801A1 - Rotor blades with vibration damping system

Info

Publication number: EP2253801A1
Application number: EP09160063A
Authority: EP
Inventors: Christoph Gerber; Jacob Laborenz; Christian Siewert; Markus Denk; Pierre-Alain Masserey
Original assignee: Alstom Technology AG
Current assignee: GE Vernova GmbH
Priority date: 2009-05-12
Filing date: 2009-05-12
Publication date: 2010-11-24
Also published as: JP2010265891A; DE102010019197A1; JP5453163B2; CN101886551A; US8376710B2; CN101886551B; US20100290893A1

Abstract

The invention relates to adjacently mounted circumferentially distributed turbo machine airfoils (2a, 2b) with vibration damping systems. Each adjacent pair of airfoils (2a, 2b) comprises a fixing and receiving portion (10a, 10b), extending between the paired adjacent airfoils (2a, 2b), each with a face (12a, 12b) that are proximal or in contact with each other. Vibration is suppressed by the fixing and receiving portions (10a, 10b) each having a received magnet (20a, 20b) fixingly installed therein and a non-magnetic conducting plate (25a) therebetween. Each magnet (20a, 20b) has a pole (22a, 22b) that faces the pole (22a, 22b) of the other magnet (20a, 20b) in between which the non-magnetic conducting plate (25a) is located and in which eddy currents can be induced by the relative movement of the magnets due to vibration.

Description

TECHNICAL FIELD

The disclosure relates to vibration damping of turbo machine airfoils. More specifically, the disclosure relates to the used of magnetic fields to damp airfoil vibration.

BACKGROUND INFORMATION

Turbo machine airfoils are subject to high static and dynamic loads due to thermal and centrifugal loads as well as dynamic excitation forces. The resulting vibration amplitudes, in combination with the high static loads, can lead to high cycle fatigue failures. Thus the damping of vibration is of great importance.
One solution to this problem is to install frictional coupling devices, such as under platform dampers, lacing wires or tip shrouds that provide damping through energy dissipation by frictional contact. This approach is disadvantaged by design complexity as physical contact parameters are difficult to evaluate and alter under operating conditions. Furthermore, the coupling of the airfoils and the geometric properties of friction damping devices change dynamic characteristics such as eigenfrequency and mode shape.
An alternative is to use the attractive force of magnets for damping. US Pat 4,722,668 , for example, discloses the use of magnets in both the shroud and at half airfoil height. The magnets are paired, wherein the magnet of one airfoil abuts a magnet fitted in an adjacent airfoil.
As an alternative over the mere use of magnets, eddy currents induced by movement of an electrical conductor in a magnetic field provides an alternative with a different damping capability. This solution uses the principle that the movement of an electrical conductor in a magnetic field induces a voltage, which in turn creates eddy currents. The magnetic field of the eddy currents opposes that of the first magnetic field thus exerting a force on the metal plate causing it to resist movement while transforming the kinetic energy of the conductor plate into heat.
DE 195 05 389 A1 for example, discloses an eddy current damping arrangement for a turbo machine in which a magnetic ring is located in a wall of a turbo-machine such that the vibration of rotating airfoils, which are equipped with an electric conductor, is suppressed when passing the ring.
US 7 399 158 B2 discloses another eddy current damping system applied to an array of airfoils mounted for rotation about a central axis. The damping arrangement includes a current carrying conductor that forms a loop around the array of airfoils.
Both of these arrangements require the installation of a magnetic ring, or ring shaped current carrying loop for inducing a magnetic field, that is separate from the airfoils. As an alternative, DE 199 37 146 A1 discloses adjacent airfoils with paired wings having ends in close proximity to each other. The end of one wing has a mounted magnet while the end of its paired opposite has a copper or aluminium plate. By this means the relative movement of the wing end is suppressed by means of the eddy current principle.
Unlike vibration suppression systems that use magnetic attraction, vibration damping by means of eddy currents requires some relative movement without which eddy currents will not be formed.

SUMMARY

Disclosed is a damping device for attenuation of vibration of airfoils, fitted in a turbo-machine, across a broad range of vibration frequency.
The disclosure attempts to address this problem by means of the subject matters of the independent claim. Advantageous embodiments are given in the dependent claims.
The present invention provides adjacently mounted circumferential distributed turbo machine airfoils that have a vibration damping system. Each adjacent pair of airfoils comprises a fixing and receiving portion on each airfoil. One extends from the first airfoil to an end defining a face, which is substantially perpendicular to the direction of extension while the other portion extends towards the first fixing and receiving portion to a face that is proximal or in contact with the face of the first fixing and receiving portion. The first portion has a first magnet, fixingly received in the first portion, with a pole facing towards the first face of the first portion and a first non-magnetic conducting plate fixingly mounted between the first face and the first magnet. The second portion has a second magnet, fixingly received in the second portion, with a pole facing the second face such that the pole is aligned with and separated, by a separation distance, from the pole of the first magnet.
The combination of paired magnets and a non-magnetic conducting plate provides higher damping capacities across a wider range of frequencies due, in part, to stronger and better aligned magnetic fields.
In damping aspects with one magnet in one fixing portion, flux lines form lines perpendicular to the face of the opposed wing resulting in a very low radial magnet field component. When two magnets face each other with unlike poles the alignment of the flux lines are qualitatively the same but with higher magnitude resulting in higher damping force. In both cases an attractive force, between magnets and the metallic portions and/ or between the magnets, is present, resulting in an unstable equilibrium created when the attractive force acting on both ends of the portions have the same magnitude. If the blade deflects to one side, the forces on the side with the smaller air gap increases whereas on the side with the bigger air gap the force decreases. This imbalance causes unstable motion. By aligning the magnets so that like poles face each other, it was found that a more stable equilibrium can be achieved. Yet further the radial magnetic flux component created between like poles was found to create an even large damping force. An aspect therefore provides that the facing poles of magnets in the receiving and fixing portions have the same polarity, for example N-N or S-S.
In another aspect the second portion also has a non-magnetic conducting plate. The non-magnetic conducting plate is fixingly mounted between the second magnet and the second face. By having a non-magnetic conducting plate in both portions the eddy current damping mechanism, for the same relative movement of the two portions, is enhanced.
In another aspect of the system a distance of between 1 mm and 5 mm separates the magnets of the two portions.
Other aspects and advantages of the present invention will become apparent from the following description, taken in connection with the accompanying drawings wherein by way of illustration and example, an embodiment of the invention is disclosed.

BRIEF DESCRIPTION OF THE DRAWINGS

By way of example, an embodiment of the present disclosure is described more fully hereinafter with reference to the accompanying drawings, in which:

Figure 1: is a perspective view of an exemplary pair of circumferentially mounted adjacent airfoils of a turbo machine according to an exemplary embodiment;
Figure 2: is a cut view through II-II of the adjacent airfoils of FIG. 1 showing an exemplary vibration damping system;
Figure 3: is an expanded view of section III of FIG. 2 showing features of an exemplary vibration damping system;
Figure 4: is an expanded view of section III of FIG. 2 showing features of another exemplary vibration damping system; and
Figure 5: is an expanded view of section III of FIG. 2 showing an arrangement where the polarity of facing magnetic poles are different.

DETAILED DESCRIPTION

Preferred embodiments of the present disclosure are now described with reference to the drawings, wherein like reference numerals are used to refer to like elements throughout. In the following description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the disclosure. It may be evident, however, that the disclosure may be practiced without these specific details.

FIG. 1 shows only two of a series of adjacently mounted circumferential distributed turbo machine airfoils 2a, 2b, where the two shown airfoils 2a, 2b, which are paired by being adjacent one another, are fitted with an exemplary vibration damping system. The adjacent airfoils 2a, 2b each have portions 10a,10b mounted on the respective airfoils 2a, 2b that extend from the airfoils 2a,2b substantially, in one exemplary embodiment, in the circumferential direction CD, and, in a not shown other exemplary embodiment, in a direction offset from the circumferential direction CD. The different extensions provide different damping characteristics. The extension of the portions 10a, 10b cause them to span the space between the airfoils 2a, 2b such that an end of the portions 10a, 10b either comes in contact with or ends in close proximity to each other at faces 12a, 12b. An important characteristic is that the portions 10a, 10b are able to move relative to each other. That is, if ends of the portions 10a, 10b are configured to be in contact with each other, the contact is such that airfoil vibration results in at least some relative movement of the portions 10, 10b. In an exemplary embodiment, shown in FIG. 1, this is achieved by the portions 10a, 10b being configured as "snubbers" 10a,10b that extend from a point part way along the radial height RD of the airfoils 2a, 2b. In a not shown exemplary embodiment this is achieved by the portions 10 extending from a radial end of the airfoils 2a, 2b so as to form airfoil tip shrouds.
FIG. 2 shows a cut view of the airfoils 2a, 2b of FIG. 1 showing paired portions 10a, 10b that form an exemplary vibration damping system. Further expanded views of exemplary portions 10a, 10b are shown in FIGs. 3 and 4. In FIG. 2 the vibration damping system comprises two paired portions, paired by proximity and interaction. Each portion 10a, 10b, in one exemplary embodiment, extends substantially in the circumferential direction CD from adjacent airfoils 2a, 2b, to distal ends that form faces 12a, 12b.The pairing, in one exemplary embodiment, is such that faces 12a, 12b of the portions 10a, 10b are substantially parallel and in close proximity to, or in contact with each other, and substantially perpendicular to the circumferential direction CD. Each portion 10a,10b fixingly receives a magnet 20a, 20b with a pole 22a, 22b such that vibrations of the airfoils 2a, 2b are mirrored by movement of the magnets 20a, 20b. Other known airfoil features such as shrouds (not shown) mounted on radially distal ends and extending between adjacent airfoils 2a, 2b may also perform the function of the exemplary fixing and receiving portions 10a, 10b. The magnets 20a, 20b are configured and arrange, in an exemplary embodiment, so that poles 22a, 22b of received magnets 20a, 20b of paired fixing and receiving portions 10a,10b substantially align in the circumferential direction CD such that one pole 22a, 22b of each magnet 20a, 20b faces one pole 22a, 22b of the other magnet 20a, 20b and that, that pole 22a, 22b also faces the face 12a, 12b of the fixing and receiving portion 10a, 10b in which it is received. This ensures a stronger and better-aligned magnetic field. The vibration damping system further comprises one or more non-magnetic conducting plates 25a, 25b fixingly mounted between the facing poles 22a, 22b of the magnets 20a, 20b, as shown in FIGs. 3 and 4.
FIG. 3 shows an exemplary embodiment in which magnets 20a, 20b are located in fixing and receiving portions 10a, 10b of adjacent airfoils 2a, 2b so as to form a vibration damping system. Each of the fixing and receiving portions 10a, 10b has a face 12a, 12b which, in an exemplary embodiment, is substantially parallel to the face 12a, 12b of a fixing and receiving portion 10a, 10b of an adjacent airfoil 2a, 2b. The proximity of the faces 12a, 12b pair the fixing and receiving portions 10a, 10b. Each of the magnets 20a,20b are aligned in the paired portions 10a, 10b, in an exemplary embodiment, in the same circumferential direction CD. The arrangement is such that one pole 22a, 22b of each magnet 20a, 20b faces the pole 22a, 22b of another magnet 20a, 20b, so as to align the poles 22a, 22b, while they face the face 12a, 12b of the fixing and receiving portion 10a, 10b in which they are received. In this way relative movement of magnets 20a, 20b mirrors movement induced by airfoil vibration while mutual attraction or rejection of the magnets 20a, 20b results in a stiffening of the adjacent airfoils 2a, 2b causing a resistance to that vibration.

Between the face 12a of one fixing and receiving portion 10a and a pole 22a of the magnet 20a received in that receiving portion 10a, an exemplary embodiment has a mounted non-magnetic conducting plate 25a. The mounting is such that the location and position of the non-magnetic conducting plate 25a is fixed relative to the magnet 20a such that vibration does not change the relative location between the non-magnetic conducting plate 25a and the magnet 20a.
The non-magnetic and conducting nature of the non-magnetic conducting plates 25a results in the formation of eddy currents in the non-magnetic conducting plate 25a when the magnet 20b in the paired fixing and receiving portion 10b moves relative to the non-magnetic conducting plate 25a. These eddy currents result in a resistance to movement that results in damping of vibration.
FIG. 4 shows an exemplary embodiment in which magnets 20a, 20b are located in fixing and receiving portions 10a, 10b of adjacent airfoils 2a, 2b so as to form a vibration damping system. Each of the fixing and receiving portions 10a, 10b has a face 12a, 12b which is substantially parallel to the face 12a, 12b of a fixing and receiving portion 10a, 10b of an adjacent airfoil 2a, 2b so by forming paired fixing and receiving portions 10a, 10b. Each of the magnets 20a, 20b are aligned in the paired portions 10a, 10b. In the exemplary embodiment shown, the portions 10a, 10b extend in the circumferential direction CD although other arrangements are possible. In any case the alignment is such that one pole 22a, 22b of each magnet 20a, 20b faces the pole 22a, 22b of another magnet 20a, 20b, so as to align the poles 22a, 22b, while they face the face 12a, 12b of the fixing and receiving portion 10a, 10b in which they are received. In this way relative movement of magnets 20a, 20b mirrors movement induced by airfoil vibration while mutual attraction or rejection of the magnets 20a, 20b results in a stiffening of the adjacent airfoils 2a, 2b causing a resistance to that vibration.
Non-magnetic conducting plates 25a, 25b are fixingly mounted between the faces 12a, 12b of each fixing and receiving portions 10a, 10b and a pole 22a, 22b of a magnet 20a, 20b within that portion 10a, 10b. That is, in the circumferential direction, extending from an airfoil 2a, 2b, each portion 10a, 10b has a received magnet 20a, 20b, a mounted non-magnetic conducting plate 25a, 25b and a face 12a, 12b. The mounting of the non-magnetic conducting plate 25a, 25b for each portion 10a, 10b is such that the location and position of the non-magnetic conducting plate 25a, 25b is fixed relative to the magnet 20a, 20b received in that portion 10a, 10b, independent of vibration.
The non-magnetic and conducting nature of the non-magnetic conducting plate 25a, 25b results in the formation of eddy currents in the non-magnetic conducting plate 25a, 25b when the magnet 20a, 20b located in the paired fixing and receiving portion 10a, 10b moves relative to the non-magnetic conducting plate 25a, 25b due to vibration. This results in a resistance to movement resulting in vibration damping. As non-magnetic conducting plates 25a, 25b are located in both paired portions 10a, 10b the damping effect, compared to an arrangement with one non-magnetic conducting plate 25a, 25b, is increased.
FIG. 5 shows an exemplary damping system that differs from that shown in FIGs. 3 and 4 by the fact that the facing poles 22a, 22b of the magnets 20a, 20b have different polarity. While a non-magnetic conducting plate 25a, 25b is shown in each portion 10a, 10b, in a not shown exemplary embodiment, only one of the portions 10a, 10b has a non-magnetic conducting plate 25a, 25b.
It was found for an arrangement comprising two adjacent airfoils 2a, 2b fitted with exemplary embodiments, the best vibration damping performance for a range of vibrational frequency can be achieved when the magnets 20a, 20b of the paired portions 10a, 10b are separated. However, as interaction of magnets 20a, 20b decreases with distance there is an optimum distance. It is assumed that this improved performance would also apply for cyclically symmetric systems were a plurality of airfoils with exemplary embodiments is circumferentially mounted albeit that the optimum separation distance SD, of between 7-10 mm determined for one experimental two airfoil 2a, 2b system is expected to reduce to between 1-5 mm for a multiple circumferential mounted airfoil 2a, 2b arrangement.
The higher the conductivity of the non-magnetic conducting plates 25a, 25b the stronger the eddy currents created by relative movement between the plates 25a, 25b and magnets 20a, 20b and therefore the greater the resilience to vibration. Therefore, in one exemplary embodiment the non-magnetic conducting plates 25a, 25b are made of material with an electrical conductivity of greater than 35 x 10⁶ S.m^-1 measured at 20°C. In another exemplary embodiment the non-magnetic conducting plates 25a, 25b are made of either or both aluminium and/or copper.
Although the disclosure has been herein shown and described in what is conceived to be the most practical exemplary embodiment, it will be appreciated by those skilled in the art that the present invention can be embodied in other specific forms without departing from the spirit or essential characteristics thereof. For example while the exemplary embodiments show only one paired fixing and receiving portions 10a, 10b per adjacent airfoils 2a, 2b, the airfoils 2a, 2b could be fitted with more than one paired portions 10a, 10b at the same and/or different radial heights RD. The presently disclosed embodiments are therefore considered in all respects to be illustrative and not restricted. The scope of the invention is indicated by the appended claims rather that the foregoing description and all changes that come within the meaning and range and equivalences thereof are intended to be embraced therein.

REFERENCE NUMBERS

2a, 2b: Airfoils
10a, 10b: Snubber (exemplary fixing and receiving portion)
12a,12b: Face
20a, 20b: Magnet
22a, 22b: Magnetic pole
25a, 25b: Non-magnetic conducting plate
CD: Circumferential direction
RH: Radial height
SD: Separation Distance

Claims

Adjacently mounted circumferential distributed turbo machine airfoils (2a, 2b) with a vibration damping system wherein each adjacent pair of airfoils (2a, 2b) consists of a first and a second airfoil (2a, 2b), the system comprises:
a first fixing and receiving portion (10a), extending from the first airfoil (2a) to an end defining a face (12a),

a second fixing and receiving portion (10b), extending towards the first fixing and receiving portion (10a) to an end defining a face (12b) proximal or in contact with the face (12a) of the first fixing and receiving portion (10a) the airfoils (2a, 2b) characterised by:

a first magnet (20a), fixingly received in the first portion (10a) and arranged such that a pole (22a) faces towards the first face (12a) of the first portion (10a);

a first non-magnetic conducting plate (25a) fixingly mounted between the first face (12a) and the first magnet (20a), and

a second magnet (20b), fixingly received in the second portion (10b) and arranged such that a pole (22b) faces the second face (12b) such that the pole (22b) is aligned with, and separated by a separation distance (SD) from, the pole (22a) of the first magnet (20a).
The airfoils of claim 1 wherein the facing poles (22a, 22b) of the first and second magnets (20a, 20b) have opposite polarity.
The airfoils of claim 1 wherein the second portion (10b) has a second non-magnetic conducting plate (25b) fixingly mounted between the second magnet (20b) and the second face (12b).
The airfoils of any one of claims 1 or 3 wherein the first magnet (20a) and the second magnet (20b) have a separated distance (SD) of between 1 mm and 5 mm.
The airfoils of any one of claims 1 to 4 wherein the first non-magnetic conducting plate (25a) and the second non-magnetic conducting plate (25b) are made of a material with an electrical conductivity of greater than 35 x 10⁶ S.m^-1 measured at 20°C.